EP3922453A1 - Nachgiebige zwischenschicht - Google Patents

Nachgiebige zwischenschicht Download PDF

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Publication number
EP3922453A1
EP3922453A1 EP21174946.0A EP21174946A EP3922453A1 EP 3922453 A1 EP3922453 A1 EP 3922453A1 EP 21174946 A EP21174946 A EP 21174946A EP 3922453 A1 EP3922453 A1 EP 3922453A1
Authority
EP
European Patent Office
Prior art keywords
plies
cmc
interlayers
matrix
various embodiments
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
EP21174946.0A
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English (en)
French (fr)
Inventor
Wayde R. Schmidt
Paul Sheedy
John A. SHARON
Neal Magdefrau
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Goodrich Corp
Original Assignee
Goodrich Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Goodrich Corp filed Critical Goodrich Corp
Publication of EP3922453A1 publication Critical patent/EP3922453A1/de
Pending legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
    • F16D65/00—Parts or details
    • F16D65/02—Braking members; Mounting thereof
    • F16D65/12—Discs; Drums for disc brakes
    • F16D65/125—Discs; Drums for disc brakes characterised by the material used for the disc body
    • F16D65/126—Discs; Drums for disc brakes characterised by the material used for the disc body the material being of low mechanical strength, e.g. carbon, beryllium; Torque transmitting members therefor
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B18/00—Layered products essentially comprising ceramics, e.g. refractory products
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B37/00—Joining burned ceramic articles with other burned ceramic articles or other articles by heating
    • C04B37/003—Joining burned ceramic articles with other burned ceramic articles or other articles by heating by means of an interlayer consisting of a combination of materials selected from glass, or ceramic material with metals, metal oxides or metal salts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
    • F16D65/00—Parts or details
    • F16D65/02—Braking members; Mounting thereof
    • F16D65/12—Discs; Drums for disc brakes
    • F16D65/125—Discs; Drums for disc brakes characterised by the material used for the disc body
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
    • F16D69/00—Friction linings; Attachment thereof; Selection of coacting friction substances or surfaces
    • F16D69/02—Composition of linings ; Methods of manufacturing
    • F16D69/023—Composite materials containing carbon and carbon fibres or fibres made of carbonizable material
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
    • F16D69/00—Friction linings; Attachment thereof; Selection of coacting friction substances or surfaces
    • F16D69/02—Composition of linings ; Methods of manufacturing
    • F16D69/027—Compositions based on metals or inorganic oxides
    • F16D69/028—Compositions based on metals or inorganic oxides containing fibres
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface 
    • B64C25/42—Arrangement or adaptation of brakes
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
    • C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
    • C04B2235/50—Constituents or additives of the starting mixture chosen for their shape or used because of their shape or their physical appearance
    • C04B2235/52—Constituents or additives characterised by their shapes
    • C04B2235/5208—Fibers
    • C04B2235/5216—Inorganic
    • C04B2235/524—Non-oxidic, e.g. borides, carbides, silicides or nitrides
    • C04B2235/5244—Silicon carbide
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
    • C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
    • C04B2235/50—Constituents or additives of the starting mixture chosen for their shape or used because of their shape or their physical appearance
    • C04B2235/52—Constituents or additives characterised by their shapes
    • C04B2235/5208—Fibers
    • C04B2235/5216—Inorganic
    • C04B2235/524—Non-oxidic, e.g. borides, carbides, silicides or nitrides
    • C04B2235/5248—Carbon, e.g. graphite
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
    • C04B2235/65—Aspects relating to heat treatments of ceramic bodies such as green ceramics or pre-sintered ceramics, e.g. burning, sintering or melting processes
    • C04B2235/66—Specific sintering techniques, e.g. centrifugal sintering
    • C04B2235/666—Applying a current during sintering, e.g. plasma sintering [SPS], electrical resistance heating or pulse electric current sintering [PECS]
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
    • C04B2235/70—Aspects relating to sintered or melt-casted ceramic products
    • C04B2235/74—Physical characteristics
    • C04B2235/77—Density
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
    • C04B2237/30—Composition of layers of ceramic laminates or of ceramic or metallic articles to be joined by heating, e.g. Si substrates
    • C04B2237/32—Ceramic
    • C04B2237/34—Oxidic
    • C04B2237/343—Alumina or aluminates
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
    • C04B2237/30—Composition of layers of ceramic laminates or of ceramic or metallic articles to be joined by heating, e.g. Si substrates
    • C04B2237/32—Ceramic
    • C04B2237/36—Non-oxidic
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
    • C04B2237/30—Composition of layers of ceramic laminates or of ceramic or metallic articles to be joined by heating, e.g. Si substrates
    • C04B2237/32—Ceramic
    • C04B2237/36—Non-oxidic
    • C04B2237/365—Silicon carbide
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
    • C04B2237/30—Composition of layers of ceramic laminates or of ceramic or metallic articles to be joined by heating, e.g. Si substrates
    • C04B2237/32—Ceramic
    • C04B2237/38—Fiber or whisker reinforced
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
    • C04B2237/30—Composition of layers of ceramic laminates or of ceramic or metallic articles to be joined by heating, e.g. Si substrates
    • C04B2237/32—Ceramic
    • C04B2237/38—Fiber or whisker reinforced
    • C04B2237/385—Carbon or carbon composite
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
    • C04B2237/50—Processing aspects relating to ceramic laminates or to the joining of ceramic articles with other articles by heating
    • C04B2237/58—Forming a gradient in composition or in properties across the laminate or the joined articles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
    • F16D65/00—Parts or details
    • F16D65/02—Braking members; Mounting thereof
    • F16D2065/13—Parts or details of discs or drums
    • F16D2065/1304—Structure
    • F16D2065/132—Structure layered
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
    • F16D2200/00—Materials; Production methods therefor
    • F16D2200/0034—Materials; Production methods therefor non-metallic
    • F16D2200/0039—Ceramics
    • F16D2200/0047—Ceramic composite, e.g. C/C composite infiltrated with Si or B, or ceramic matrix infiltrated with metal
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
    • F16D2200/00—Materials; Production methods therefor
    • F16D2200/006—Materials; Production methods therefor containing fibres or particles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
    • F16D2200/00—Materials; Production methods therefor
    • F16D2200/0078—Materials; Production methods therefor laminated
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
    • F16D2250/00—Manufacturing; Assembly
    • F16D2250/0061—Joining

Definitions

  • the present disclosure relates to aircraft wheel and brake systems and, more particularly, to layered components having plies interleaved with compliant interlayers for use within aircraft brake systems and other apparatus.
  • Aircraft typically utilize brake systems or mechanisms on wheels to slow or stop the aircraft during landings, taxiing and emergency situations, such as, for example, a rejected takeoff (RTO), which generally refers to application of a brake mechanism during an aborted takeoff and involves high braking loads over a short time period, resulting in a rapid increase in the brake temperature.
  • RTO rejected takeoff
  • a brake mechanism generally employs a heat sink comprising a series of friction disks, sandwiched between a pressure plate and an end plate, that may be forced into sliding contact with one another during a brake application to slow or stop the aircraft. Under various conditions, such brake applications may generate high temperatures and frictional loads throughout the heat sink and particularly on the surfaces of the stators and rotors and the pressure plate and the end plate that comprise the heat sink.
  • Carbon/carbon (C/C) composite or ceramic matrix composite (CMC) structures for example, comprise a plurality of either fiber-based plies, foam or other porous structures layered into a preform which may then be densified and machined to a final form.
  • CVI chemical vapor infiltration
  • MI melt infiltration
  • PIP polymer infiltration and pyrolysis
  • hot pressing or glass transfer molding, each independently or in conjunction for densification of the C/C or CMC structure.
  • the present techniques are, however, limited in their ability to produce C/C or CMC structures or materials capable of withstanding temperatures on the order of 2550 °F ( ⁇ 1400 °C) or greater in oxidizing or combustion environments.
  • Traditional bulk densification of C/C or CMC preforms by CVI tends to induce thermal stresses, mechanical stresses, or shrinkage, as well as density gradients, with such issues generally increasing in proportion to the preform thickness.
  • techniques to improve the bonds between adjacent laminates are advantageous for improving the strength of the resulting composite and its ability to withstand the stresses and high temperatures experienced during operation.
  • the brake component includes a ceramic matrix composite (CMC) structure including a plurality of nominally dense plies, interleaved with a plurality of interlayers, wherein the plurality of nominally dense plies and the plurality of interlayers are bonded by at least one of a Field Assisted Sintering Technique (FAST), a Spark Plasma Sintering (SPS) process, a radiative heating process, or a localized Joule heating process.
  • FAST Field Assisted Sintering Technique
  • SPS Spark Plasma Sintering
  • the brake component is a rotor disk or a stator disk.
  • the CMC structure comprises at least one of a silicon-carbide fiber/silicon-carbide matrix, a carbon fiber/carbon matrix or a carbon fiber/silicon-carbide matrix. In various embodiments, the CMC structure comprises at least one of an alumina matrix, a mullite matrix or a zirconium diboride matrix. In various embodiments, the CMC structure comprises one or more compositions, including, borides, carbides, oxides, phosphides, nitrides or mixed phases, including oxynitrides or oxycarbides; carbon or silicon-based compositions; refractory metal carbides; or silica and phosphate-based glasses or glass ceramics.
  • the plurality of interlayers comprises forcespun or electrospun nanofiber mats or nanowire metal meshes. In various embodiments, the plurality of interlayers comprises nonwoven fabrics made of preceramic polymer nanofibers or polyacrylonitrile nanofibers. In various embodiments, the plurality of interlayers comprises at least one of a particulate, a chopped fiber, a nanotube, resin, or a slurry.
  • the CMC structure is characterized by a gradation of a CMC composition among the plurality of nominally dense plies.
  • the gradation of the CMC composition is defined between a braking surface and a core layer of a rotor disk or a stator disk.
  • one or more of the plurality of nominally dense plies of the CMC structure comprises greater than sixty percent by volume of fiber.
  • at least one of the plurality of nominally dense plies comprises a monolithic ceramic composition.
  • the article of manufacture includes a ceramic matrix composite (CMC) structure including a plurality of nominally dense plies, interleaved with a plurality of interlayers, wherein the plurality of nominally dense plies and the plurality of interlayers are bonded by at least one of a Field Assisted Sintering Technique (FAST), a Spark Plasma Sintering (SPS) process, a radiative heating process or a localized Joule heating process.
  • CMC ceramic matrix composite
  • FAST Field Assisted Sintering Technique
  • SPS Spark Plasma Sintering
  • the CMC structure comprises at least one of a silicon-carbide fiber/silicon-carbide matrix, a carbon fiber/carbon matrix, a carbon fiber/silicon-carbide matrix, an alumina matrix, a mullite matrix, or a zirconium diboride matrix.
  • the CMC structure comprises one or more compositions, including, borides, carbides, oxides, phosphides, nitrides or mixed phases, including oxynitrides or oxycarbides; carbon or silicon-based compositions; refractory metal carbides; or silica and phosphate-based glasses or glass ceramics.
  • the plurality of interlayers comprises forcespun or electrospun nanofiber mats or nanowire metal meshes. In various embodiments, the plurality of interlayers comprises nonwoven fabrics made of preceramic polymer nanofibers or polyacrylonitrile nanofibers. In various embodiments, the plurality of interlayers comprises at least one of a particulate, a chopped fiber, a nanotube, a resin or a slurry.
  • the CMC structure is characterized by a gradation of a CMC composition among the plurality of nominally dense plies.
  • one or more of the plurality of nominally dense plies of the CMC structure comprises greater than sixty percent by volume of fiber.
  • at least one of the plurality of nominally dense plies comprises a monolithic ceramic composition.
  • a method of manufacturing a layered component includes densifying a feedstock to generate a plurality of nominally dense plies; assembling the plurality of nominally dense plies, interleaved with a plurality of interlayers, to generate a preform structure; and bonding the preform structure via at least one of a Field Assisted Sintering Technique (FAST), a Spark Plasma Sintering (SPS) process, or a localized heating process.
  • FAST Field Assisted Sintering Technique
  • SPS Spark Plasma Sintering
  • any reference to attached, fixed, connected, or the like may include permanent, removable, temporary, partial, full or any other possible attachment option. Additionally, any reference to without contact (or similar phrases) may also include reduced contact or minimal contact.
  • distal refers to a direction outward, or generally away, from a reference component and "proximal” or “proximate” refer to a direction inward, or generally, towards the reference component. All ranges may include upper and lower values and all ranges and ratio limits disclosed herein may be combined. Further, the term “about” is intended to include a degree of error associated with measurement of a particular quantity based upon equipment or techniques otherwise available at the time of filing the application. For example, “about” may include a range of ⁇ 5% or 2% of a given value.
  • the aircraft 10 includes landing gear, which may include a left main landing gear 12, a right main landing gear 14 and a nose landing gear 16.
  • the landing gear support the aircraft 10 when it is not flying, allowing the aircraft 10 to taxi, take off and land without damage. While the disclosure refers to the three landing gear configurations just described, the disclosure nevertheless contemplates any number of landing gear configurations.
  • FIG. 1B there is schematically depicted a brake mechanism 100 configured for use on a landing gear, such as, for example, each of the left main landing gear 12 and the right main landing gear 14 described above with reference to FIG. 1A .
  • the brake mechanism 100 surrounds an axle 102 having a wheel 104 disposed thereon and configured to rotate about the axle 102 via one or more bearing assemblies 103.
  • the wheel 104 includes a wheel web 105 and a wheel well 107, with the wheel well being generally cylindrical and coaxial with respect to a rotational axis (or a central axis 106) of the wheel.
  • the central axis 106 extends through the axle 102 and defines a center of rotation of the wheel 104.
  • a torque plate barrel 108 (sometimes referred to as a torque tube or barrel or a torque plate) is aligned concentrically with the central axis 106, and the wheel 104 is rotatable relative to the torque plate barrel 108.
  • the wheel 104 and the brake mechanism 100 comprise a wheel and brake assembly.
  • the brake mechanism 100 includes an actuator ram assembly 110, a pressure plate 112 disposed adjacent the actuator ram assembly 110, an end plate 114 positioned a distal location from the actuator ram assembly 110, and a plurality of rotor disks 116 interleaved with a plurality of stator disks 118 positioned intermediate the pressure plate 112 and the end plate 114.
  • the pressure plate 112, the plurality of rotor disks 116, the plurality of stator disks 118 and the end plate 114 together form a brake heat sink or a brake stack 120.
  • the pressure plate 112, the end plate 114 and the plurality of stator disks 118 are mounted to the torque plate barrel 108 and remain rotationally stationary relative to the axle 102.
  • the plurality of rotor disks 116 is mounted to the wheel 104 and rotate with respect to each of the pressure plate 112, the end plate 114 and the plurality of stator disks 118.
  • An actuating mechanism for the brake mechanism 100 includes a plurality of actuator ram assemblies, including the actuator ram assembly 110, circumferentially spaced around a piston housing 122 (only one actuator ram assembly is illustrated in FIG. 1B ).
  • the plurality of actuator ram assemblies affects a braking action by urging the pressure plate 112 and the plurality of stator disks 118 into frictional engagement with the plurality of rotor disks 116 and against the end plate 114.
  • the resulting frictional contact slows or stops or otherwise prevents rotation of the wheel 104.
  • the plurality of rotor disks 116 and the plurality of stator disks 118 are fabricated from various materials, such as, for example, carbon-carbon or ceramic matrix composite materials, that enable the brake disks to withstand and dissipate the heat generated during and following a braking action.
  • the actuator ram assemblies may comprise electrically operated actuator rams or hydraulically operated actuator rams, although some brakes may use pneumatically operated actuator rams.
  • the actuator ram assemblies may be coupled to a power source via a brake servo valve (BSV) and a shutoff valve (SOV).
  • BSV brake servo valve
  • SOV shutoff valve
  • the SOV effectively functions as a shutoff valve, where in a first position (e.g. , an armed position), fluid pressure is permitted to pass through the valve, and where in a second position (e.g., a disarmed position) fluid pressure is restricted or prevented from passing through the valve.
  • a brake controller (or controller) is coupled to one or more electromechanical actuator controllers (EMAC) for a brake, which drives one or more electromechanical brake actuators.
  • EMAC electromechanical actuator controllers
  • the brake controller may be in communication with a brake pedal, and thus may control the EMAC in accordance with pilot or copilot braking commands.
  • a brake controller may comprise a processor and a tangible, non-transitory memory.
  • the brake controller may comprise one or more logic modules that implement brake logic.
  • the brake controller may comprise other electrical devices to implement brake logic.
  • a CMC structure may be one or more of the pressure plate 112, the end plate 114, the plurality of rotor disks 116 and the plurality of stator disks 118.
  • brake components the processes and techniques described herein are applicable to any number of other structures such as, for example, gas turbine engine components, including, without limitation, airfoils, blades, vanes, disks, nozzles, heat exchangers, diffusers and combustors components.
  • the processes and techniques described herein are applicable to other articles of manufacture, including, for example, seals, rotors, cases, heatshields, beams and plates. Accordingly, the disclosure should be interpreted as applying to myriad articles of manufacture and not be limited to fabrication of brake components.
  • a layered structure 200 prior to bonding, is illustrated having a plurality of nominally dense plies 202 (or laminates) interleaved with a plurality of interlayers 204 (or compliant interlayers), in accordance with various embodiments.
  • a first ply 206 and a second ply 208 are interleaved by a first interlayer 207 and a third ply 210 and a fourth ply 212 are interleaved by a second interlayer 211.
  • the plurality of nominally dense plies 202 may comprise a ceramic matrix composite (CMC) structure such as, for example, a silicon-carbide fiber/silicon-carbide matrix, a carbon fiber/carbon matrix, or a carbon fiber/silicon-carbide matrix.
  • CMC ceramic matrix composite
  • the plurality of nominally dense plies is characterized by an open or surface porosity of less that about 20% or less than about 5%; or, alternatively, by an apparent density of about 80% to about 100% or about 95% to about 100% of the theoretical maximum density for a CMC composition selected for densification.
  • the CMC structure including either or both of the matrices and the fibers, may include one or more of, without limitation, alumina (e.g., an alumina matrix), mullite (e.g., a mullite matrix), or zirconium diboride (e.g., a zirconium diboride matrix).
  • alumina e.g., an alumina matrix
  • mullite e.g., a mullite matrix
  • zirconium diboride e.g., a zirconium diboride matrix
  • the CMC structure may comprise one or more of borides, carbides, oxides, phosphides, nitrides or mixed phases including oxynitrides, oxycarbides and the like; carbon or silicon-based compositions; refractory metal carbides; silica and phosphate-based glasses or glass ceramics; and oxides, including, for example, aluminum oxide, zirconium oxide or zirconium dioxide, hafnium oxide, rare earth oxides, or combinations thereof.
  • the borides may be selected among a group comprising: ZrB 2 , HfB 2 , VB 2 , TiB 2 , TaB 2 , TaB, NbB 2 , NbB, CrB 2 , Mo 2 B 5 , W 2 B 5 , Fe 2 B, FeB, Ni 2 B, NiB, LaB 6 , CoB, Co 2 B, or any other refractory boride.
  • the carbides may be selected among a group comprising: SiC, HfC, ZrC, C, B 4 C, SiOC, SiBCN, TiC, WC, Mo 2 C, TaC, NbC, or any other refractory carbide.
  • the oxides may be selected among a group comprising: HfO 2 , ZrO 2 , Al 2 O 3 , SiO 2 , class compositions including aluminosilicates, borosilicates, lithium aluminosilicates (LAS), magnesium aluminosilicates, barium magnesium aluminosilicates (BMAS), calcium aluminosilicates or other silica containing high temperature glasses, or other mixed metal oxides.
  • class compositions including aluminosilicates, borosilicates, lithium aluminosilicates (LAS), magnesium aluminosilicates, barium magnesium aluminosilicates (BMAS), calcium aluminosilicates or other silica containing high temperature glasses, or other mixed metal oxides.
  • the nitrides may be selected among a group comprising: AlN, Si 3 N 4 , SiAlON, TaN, TiN, TiAIN, W 2 N, WN, WN 2 , VN, ZrN, BN, HfN, NbN, or any other refractory nitrides.
  • the CMC structure may comprise mixed refractory nonoxides such as, for example, SiCN. While the disclosure focuses on the plurality of nominally dense plies 202 comprising CMC structures, the disclosure is not so limited and contemplates the plurality of nominally dense plies 202 comprising other materials, such as, for example, metallic materials.
  • the plurality of interlayers 204 may comprise one or more of a variety of compliant materials or structures, including, for example, forcespun or electrospun nanofiber mats, nanowire metal meshes or mats, green fiber mats, cured fiber mats, flexible preceramic resin films, flexible ceramic, glass or metal films, porous films, photocurable filled systems, self-leveling fluids, preceramic-based nanofiber cloth, carbon films and cloth or similar compliant materials or structures.
  • compliant materials or structures including, for example, forcespun or electrospun nanofiber mats, nanowire metal meshes or mats, green fiber mats, cured fiber mats, flexible preceramic resin films, flexible ceramic, glass or metal films, porous films, photocurable filled systems, self-leveling fluids, preceramic-based nanofiber cloth, carbon films and cloth or similar compliant materials or structures.
  • the plurality of interlayers may comprise flexible nonwoven fabrics made of preceramic polymer nanofibers (e.g., SiOC, SiC, Si 3 N 4 or the like), polyacrylonitrile nanofibers, or other carbon-precursor based nanofibers.
  • the plurality of interlayers may comprise submicron or micron-scale thick foils of metal, ceramic or glass.
  • the plurality of interlayers comprises at least one of a particulate, a chopped fiber, a nanotube, a resin or a slurry.
  • the nanofibers within the interlayers include carbide-, nitride-, oxycarbide-, oxynitride-, carbonitride-, silicate-, boride-, phosphide-, or oxide-based fibers.
  • the fibers are fully crystalline, partially crystalline or predominantly amorphous or glassy.
  • the plurality of interlayers may comprise mats fabricated from other materials, including, for example, tape cast sheets comprising a resin, particulates, continuous or chopped fibers (nanofiber or otherwise), or nanotubes or the like.
  • the interlayers provides several functional advantages to the layered structure 200, either during fabrication or following fabrication and while in use (e.g., as a rotor or stator within a brake mechanism).
  • Various of the advantages include, for example, a reduction in asperities between adjacent pairs of plies or laminates, the ability to drape the interlayer over irregularly shaped surfaces or multiple surfaces, the ability to conform to surface irregularities, the ability to fill voids between adjacent pairs of plies or laminates, the ability to provide a compositional change to the fabricated layered structure, and the ability to densify joints between adjacent pairs of plies or laminates.
  • the interlayers may be fabricated independently of the plies or laminates and, upon assembly and bonding, the interlayers enable an intimate contact to be established between the plies or laminates.
  • a layered structure 300 prior to bonding, is illustrated having a plurality of nominally dense plies, including, for example, a first ply 302, a second ply 304, a third ply 306, a fourth ply 308 and a fifth ply 310, interleaved by a plurality of compliant interlayers, including, for example, a first interlayer 303, a second interlayer 305, a third interlayer 307 and a fourth interlayer 309, respectively.
  • the pluralities of plies and interlayers are similar to the plurality of nominally dense plies 202 and the plurality of interlayers 204 described above with reference to FIG. 2 .
  • a layered component 312, as illustrated in FIG. 3B may be machined or otherwise processed into a final form, such as, for example, a brake component.
  • machining of the plies may take place prior to assembly and bonding, or both prior to and after assembly and bonding.
  • each of the plies (302, 304, 306, 308, 310) is densified to a nominal density prior to arrangement with the interlayers (303, 305, 307, 309) for assembly.
  • the plies may be densified by one or more of any of the densification techniques known to those skilled in the art, such as, for example, PIP, CVI, MI, chemical vapor deposition (CVD), slurry casting, atomic layer deposition (ALD), hot pressing, glass transfer molding, or the like.
  • an ALD process is employed to enable a more complete densification of the plies (or the feedstock) prior to bonding.
  • the ALD process works by first adsorbing a nominal (mono)layer of a precursor on one or more surfaces of the feedstock (e.g., a fiber based structure such as a ply, a layer or a foam structure), purging the excess precursor, and then introducing a second reactant that converts the adsorbed layer to the desired chemistry.
  • a nominal (mono)layer of a precursor on one or more surfaces of the feedstock (e.g., a fiber based structure such as a ply, a layer or a foam structure), purging the excess precursor, and then introducing a second reactant that converts the adsorbed layer to the desired chemistry.
  • the reaction conditions are chosen to achieve the best combination of precursor adsorption and subsequent reaction, with typical growth per cycle in the
  • Compositions can vary from metals to oxides and other ceramics (e.g., borides, carbides, nitrides or the like as described above), multilayer structures and even polymers such as, for example, by means of Molecular Layer Deposition (MLD).
  • MLD Molecular Layer Deposition
  • ALD coating processes such as, for example, those used for Al 2 O 3 , may be used to deposit several tens of microns of material.
  • the plies (302, 304, 306, 308, 310) (or a plurality of nominally dense plies) may be produced utilizing higher throughput ALD techniques such as spatial ALD.
  • the feedstock plies may be densified via any suitable rapid processing densification technique in continuous or batch operations.
  • the ALD process tends to enable substantially uniform build-up of material on exposed surfaces, throughout high aspect ratio substrates (including, for example, fibers, microcracks, and gaps) and even among several preform parts in a deposition chamber.
  • ALD would tend to enable more uniform filling of a CMC structure (or any fiber, particulate, or other type of preform or substrate or feedstock) and therefore tends to inhibit "canning off' or to facilitate a substantial reduction in "canning off' of the feedstock based purely on geometric considerations.
  • CMC feedstock preforms may possess geometries tending to promote densification at the feedstock surface, tending thereby to accelerate surface deposition and tending thereby to inhibit interior densification of the preform (e.g., by closing gas paths to the preform interior).
  • the interior of a preform may be "canned off' from the surface layers tending thereby to seal it from further densification, creating a density gradient in the component.
  • the deposition rate for ALD (with sufficient time for diffusion) also does not change due to the process being an inherently self-limiting surface reaction.
  • a CVI or CVD densification process may result in a density gradient from outside-in (e.g., from diffusional processes) and, due to geometrical constraints, may result in a more rapid reaction and "canning-off' of a pore structure of the feedstock.
  • ALD tends to continue to uniformly and completely fill the pore structure due to being a series of self-limiting surface reactions which do not result in non-uniform nucleation and growth of the deposited material as is seen in CVI processes.
  • utilizing a reduced feedstock volume may tend to improve part densification.
  • the ALD process tends to enable manufacture of CMC structures with relatively higher fiber or other reinforcement content loading (e.g., structures comprising greater than sixty percent (60%) by volume fiber or other reinforcement) than the other densification processes described herein.
  • ALD densification of feedstock plies may tend to improve the mechanical properties of CMC structures.
  • feedstock plies may be cut to shape, machined or laid up in a mold prior to densification thereby enabling production of nominally dense plies of arbitrary shape or curvature.
  • individual feedstock plies may be densified in a mold having an annular shape for a brake component or a mold having the curvature of an airfoil to generate a nominally dense ply having an annular structure or an airfoil curvature.
  • each of the nominally dense plies (302, 304, 306, 308, 310) may be layered and bonded at contact interfaces between each of the plies to form the layered component 312 (e.g., a uniform CMC structure) comprising the bonded layers of nominally dense plies (302, 304, 306, 308, 310) interleaved with the interlayers (303, 305, 307, 309).
  • the layered component 312 e.g., a uniform CMC structure
  • first ply 302 and the second ply 304 may make surface contact with the first interlayer 303 at contact interfaces and bonded via at least one of a Field Assisted Sintering Technique (FAST), a Spark Plasma Sintering (SPS) process, or a similar method that facilitates localized heating at the contact interfaces to be bonded.
  • FAST Field Assisted Sintering Technique
  • SPS Spark Plasma Sintering
  • Each of the remaining plies and interlayers may similarly be bonded via the localized heating process to build up the layered component.
  • the interlayers promote bonding and enhance interlaminar properties (e.g., mechanical, thermal, electrical or the like) of the layered component 312.
  • the interlayers may comprise a particulate, a chopped fiber, a nanotube, a slurry or the like.
  • Exemplary particulate compositions include those previously described for carbides, oxides, nitrides and borides, and include morphologies ranging from spherical or acicular to elongated, and sizes ranging from nanometer or submicron to tens of microns.
  • Exemplary chopped fibers include carbon, silicon carbide, silicon nitride, silicon oxycarbide and oxides.
  • Exemplary slurries may be aqueous or organic solvent based suspensions or dispersions of ceramic, metal or carbonaceous particulates.
  • a layered structure 400 prior to bonding, is illustrated having a plurality of nominally dense plies, including, for example, a first ply 402, a second ply 404, a third ply 406, a fourth ply 408 and a fifth ply 410, interleaved by a plurality of interlayers, including, for example, a first interlayer 403, a second interlayer 405, a third interlayer 407 and a fourth interlayer 409, respectively.
  • the pluralities of plies and interlayers are similar to the plurality of nominally dense plies 202 and the plurality of interlayers 204 described above with reference to FIG. 2 .
  • the plies (402, 404, 406, 408, 410) and the interlayers (403, 405, 407,409) may be bonded to form a sandwich-like CMC structure defined by a set of core plies (404, 406, 408) (or inner plies, shown in light shade) of a first CMC composition (e.g., a SiC/SiC composition) and a set of face plies (402, 410) (or outer plies, shown in dark shade) of a second CMC composition (e.g., an ultra-high temperature ceramic (UHTC) composition, an environmental barrier coating (EBC) composition or a thermal barrier coating (TBC) composition).
  • UHTC ultra-high temperature ceramic
  • EBC environmental barrier coating
  • TBC thermal barrier coating
  • a CMC composition may include a monolithic ceramic composition (e.g., a non-fiber reinforced composition).
  • the core plies (404, 406, 408) may have an alternating fiber orientation whereby the fibers of each of the respectively adjacent plies are set at a non-parallel relative angle.
  • the fibers within a center core ply (406) may be set at an angle of zero degrees (0°) relative to a reference direction, while the fibers within each of the respectively adjacent core plies (404, 408) may be set orthogonal (or at ninety degrees (90°)) with respect to the fibers within the center core ply (406).
  • the structure just described may be used in a brake component, such as, for example, a rotor disk or a stator disk, with the face plies (402, 410) (e.g., a frictional surface or a braking surface) constructed of an ultra-high temperature composition (e.g., a UHTC composition) and the core plies (or the core of the rotor disk or the stator disk) constructed of a relatively lower temperature composition (e.g., a SiC/SiC composition).
  • a brake component such as, for example, a rotor disk or a stator disk, with the face plies (402, 410) (e.g., a frictional surface or a braking surface) constructed of an ultra-high temperature composition (e.g., a UHTC composition) and the core plies (or the core of the rotor disk or the stator disk) constructed of a relatively lower temperature composition (e.g., a SiC/SiC composition).
  • UHTC composition ultra-high
  • a layered structure 420 prior to bonding, is illustrated having a plurality of plies, including, for example, a first ply 422, a second ply 424, a third ply 426, a fourth ply 428 and a fifth ply 430, interleaved by a plurality of interlayers, including, for example, a first interlayer 423, a second interlayer 425, a third interlayer 427 and a fourth interlayer 429, respectively.
  • the pluralities of plies and interlayers are similar to the plurality of nominally dense plies 202 and the plurality of interlayers 204 described above with reference to FIG. 2 .
  • the plies (422, 424, 426, 428, 430) and the interlayers (423, 425, 427,429) may be bonded to form a gradated-like CMC structure defined by a gradation between a ply (422) having a relatively lower temperature CMC composition and a ply (430) having a UHTC CMC composition or a EBC or TBC composition.
  • the CMC composition of the plurality of plies (422, 424, 426, 428, 430), interleaved by the plurality of interlayers (423, 425, 427,429), may vary along a gradient (illustrated as a lighter to a darker shade of the plies) defined from the low temperature CMC plies and increasing to the high temperature CMC plies.
  • a gradated CMC structure such as, for example, a combustor liner, may be optimized to include relatively high temperature CMC compounds proximate a flame front and relatively low temperature CMC compounds away from the flame front.
  • a turbine vane or blade may be fabricated to comprise the relatively high temperature CMC compounds proximate an aerodynamic surface and the relatively low temperature CMC compounds or plies proximate a core layer, with a gradated-like structure therebetween.
  • a CMC structure may be optimized for compositions tending thereby to reduce material costs and production costs and time while tending to increase mechanical and thermal performance of the CMC structure.
  • the gradation may be tailored for any number of desirable physical, thermal, electrical, material, and mechanical properties including, but not limited to coefficient of thermal expansion, toughness, hardness, strength, friction and wear performance, thermal and electrical conductivities, elastic modulus, heat capacity, oxidation behavior and density.
  • one or more of the interlayers (423, 425, 427,429), particularly the interlayers adjacent a wear surface, may prove advantageous in repair or refurbishment operations. For example, if a brake wear surface becomes worn through use, then the ply (or plies) that forms the wear surface may be machined away and replaced with a new interlayer and ply (or interlayers and plies), assembled and bonded to the outer surface that results following the machining away, thereby forming a new wear surface.
  • the plurality of plies 442 may include nominally dense plies as described above, interleaved by a plurality of compliant interlayers.
  • the pluralities of plies and interlayers are similar to the plurality of nominally dense plies 202 and the plurality of interlayers 204 described above with reference to FIG. 2 .
  • the plurality of nominally dense plies 442 and, if incorporated, the plurality of compliant interlayers may be bonded to form a gradated-like CMC structure similar to those described above with reference to FIGS.
  • the layered structure 440 is bonded using, for example, a FAST process to generate a layered structure 444.
  • the layered structure 444 may be machined to generate a layered component or to generate layered subcomponents for subsequent assembly.
  • the layered component 444 may be cut into a plurality of sublayers 446 having gradated properties similar to those described above, the cuts being made along a plurality of cutting planes 445.
  • the plurality of sublayers 446 may be reoriented (e.g., rotated with respect to one another) into a modified layered structure 448.
  • one or more compliant interlayers 450 are interleaved within the modified layered structure 448 and a second bonding process (e.g., a FAST process) is applied.
  • the resulting layered structure or component may thus be tailored with specialized gradated properties in different directions and at different locations throughout the resulting layered structure to provide specialized thermal or structural attributes of the final component.
  • a first step 502 includes performing a densification of a feedstock ply to generate a nominally dense ply.
  • the nominally dense ply may have an apparent density between ninety percent (90%) and one-hundred percent (100%) of the theoretical maximum density for a CMC composition selected for densification of the feedstock ply.
  • a second step 504 may include assembling a plurality of nominally dense plies, interleaved by a plurality of interlayers, to generate a preform structure.
  • a third step 506 includes bonding the preform structure to generate a layered structure.
  • the third step 506 includes bonding the preform structure via a FAST process, an SPS process, a radiative heating process, a Joule heating process or a similar process or method that facilitates a localized heating at the bonding interface between the plies and the interlayers.
  • a fourth step 508 includes performing a secondary densification process to the layered structure subsequent to the bonding process such as, for example, an ALD or a CVD densification process.
  • the secondary densification may also occur during the bonding operation (e.g., during the FAST process) of the third step 506.
  • a fifth step 510 includes finishing or machining the layered structure or applying a surface coating to the layered structure to generate the layered component.
  • machining of the plies may take place prior to or between the assembly and bonding steps, or both prior to or between and after the assembly and bonding steps.
  • references to "one embodiment,” “an embodiment,” “various embodiments,” etc. indicate that the embodiment described may include a particular feature, structure, or characteristic, but every embodiment may not necessarily include the particular feature, structure, or characteristic. Moreover, such phrases are not necessarily referring to the same embodiment. Further, when a particular feature, structure, or characteristic is described in connection with an embodiment, it is submitted that it is within the knowledge of one skilled in the art to affect such feature, structure, or characteristic in connection with other embodiments whether or not explicitly described. After reading the description, it will be apparent to one skilled in the relevant art(s) how to implement the disclosure in alternative embodiments.
  • system program instructions or controller instructions may be loaded onto a tangible, non-transitory, computer-readable medium (also referred to herein as a tangible, non-transitory, memory) having instructions stored thereon that, in response to execution by a controller, cause the controller to perform various operations.
  • a tangible, non-transitory, computer-readable medium also referred to herein as a tangible, non-transitory, memory
  • non-transitory is to be understood to remove only propagating transitory signals per se from the claim scope and does not relinquish rights to all standard computer-readable media that are not only propagating transitory signals per se.

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4095114A1 (de) * 2021-04-21 2022-11-30 Honeywell International Inc. Hochtemperaturschnittstellen für keramische verbundwerkstoffe
US12071383B2 (en) 2021-04-21 2024-08-27 Honeywell International Inc. Contact joule heating for sintering high temperature coatings

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2617132A (en) * 2022-03-30 2023-10-04 Airbus Operations Ltd A brake component

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20180335099A1 (en) * 2017-05-16 2018-11-22 Goodrich Corporation Rapid ceramic matrix composite fabrication of aircraft brakes via field assisted sintering
EP3712122A1 (de) * 2019-03-21 2020-09-23 United Technologies Corporation Systeme und verfahren für generativ gefertigte keramische verbundstoffe
EP3805187A1 (de) * 2019-10-08 2021-04-14 Goodrich Corporation Herstellung von flugzeugbremsen aus keramikmatrix-verbundwerkstoff mit hoher wärmekapazität durch funkenplasmasintern

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5199481A (en) * 1988-10-17 1993-04-06 Chrysler Corp Method of producing reinforced composite materials
JP4279221B2 (ja) * 2004-09-10 2009-06-17 日信工業株式会社 複合金属材料及びその製造方法、キャリパボディ、ブラケット、ディスクロータ、ドラム並びにナックル
US7393559B2 (en) 2005-02-01 2008-07-01 The Regents Of The University Of California Methods for production of FGM net shaped body for various applications
US9005755B2 (en) * 2007-01-03 2015-04-14 Applied Nanostructured Solutions, Llc CNS-infused carbon nanomaterials and process therefor
JP5116082B2 (ja) 2007-04-17 2013-01-09 住友精密工業株式会社 高熱伝導複合材料
US20140287641A1 (en) * 2013-03-15 2014-09-25 Aerogel Technologies, Llc Layered aerogel composites, related aerogel materials, and methods of manufacture
US20150183691A1 (en) 2014-01-02 2015-07-02 Steffen Walter Manufacturing method and repairing method
US11097511B2 (en) 2014-11-18 2021-08-24 Baker Hughes, A Ge Company, Llc Methods of forming polymer coatings on metallic substrates
US12030820B2 (en) * 2019-08-09 2024-07-09 Rtx Corporation High temperature fiber, method of making and high temperature fiber composites
US12071378B2 (en) * 2019-08-09 2024-08-27 Rtx Corporation High temperature fiber and method of making
US11293507B2 (en) * 2019-10-08 2022-04-05 Honeywell International Inc. Composite fiber preform for disc brakes

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20180335099A1 (en) * 2017-05-16 2018-11-22 Goodrich Corporation Rapid ceramic matrix composite fabrication of aircraft brakes via field assisted sintering
EP3712122A1 (de) * 2019-03-21 2020-09-23 United Technologies Corporation Systeme und verfahren für generativ gefertigte keramische verbundstoffe
EP3805187A1 (de) * 2019-10-08 2021-04-14 Goodrich Corporation Herstellung von flugzeugbremsen aus keramikmatrix-verbundwerkstoff mit hoher wärmekapazität durch funkenplasmasintern

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
LI RAN ET AL: "FABRICATION OF SHORT-CF/SIC FUNCTIONALLY GRADED MATERIALS", MATERIALS SCIENCE FORUM, TRANS TECH PUBLICATIONS LTD- SWITZERLAND, CH, vol. 423-425, 15 October 2005 (2005-10-15), pages 253 - 256, XP001248759, ISSN: 0255-5476 *
WANG HAI-LONG ET AL: "Preparation and mechanical properties of laminated zirconium diboride/molybdenum composites sintered by spark plasma sintering", FRONTIERS OF MATERIALS SCIENCE IN CHINA, vol. 3, no. 3, 24 June 2009 (2009-06-24), pages 273 - 280, XP055847238, ISSN: 1673-7377, Retrieved from the Internet <URL:http://link.springer.com/article/10.1007/s11706-009-0050-z/fulltext.html> DOI: 10.1007/s11706-009-0050-z *

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4095114A1 (de) * 2021-04-21 2022-11-30 Honeywell International Inc. Hochtemperaturschnittstellen für keramische verbundwerkstoffe
US11866377B2 (en) 2021-04-21 2024-01-09 Honeywell International Inc. High temperature interfaces for ceramic composites
US12071383B2 (en) 2021-04-21 2024-08-27 Honeywell International Inc. Contact joule heating for sintering high temperature coatings

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